Author
Pengnian Yang
Bio: Pengnian Yang is an academic researcher from National University of Defense Technology. The author has contributed to research in topics: Scramjet & Combustion. The author has an hindex of 1, co-authored 7 publications receiving 4 citations.
Topics: Scramjet, Combustion, Combustor, Ramjet, Specific impulse
Papers
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TL;DR: In this paper, the influence of three different injection structures on the performance of a solid scramjet was investigated using direct-connect tests using a boron-based fuel-rich propellant and simulated a flight Mach number 5.6 at 25 km.
8 citations
TL;DR: In this paper, an efficient performance evaluation method based on ground direct-connected test was developed, which can determine the performance parameters of the scramjet combustor (internal resistance, combustion efficiency, and total pressure recovery coefficient) and that (specific impulse and thrust) of the overall scramjet during the working time under the assumptions of adiabatic inlet and adiabaatic-isentropic nozzle.
8 citations
TL;DR: In this article, the effects of equivalence ratio and solid propellant composition on the ignition delay time of fuel-rich mixture in solid rocket scramjets were experimentally investigated for the first time.
6 citations
TL;DR: In this article, a modular solid scramjet combustor with multicavity was proposed, which can effectively solve the ignition delay problem of the fuel-rich mixture, and the narrow/lobe cavity shows the ability to improve the mixing and combustion of the mixture.
Abstract: In this paper, a modular solid scramjet combustor with multicavity was proposed. The influence of multicavity shape on the performance of solid scramjet was investigated by the direct-connected tests. The experiments simulated a flight Mach 5.5 at 25 km. The boron-based fuel-rich propellant was used. The microstructure of combustion products was analyzed by SEM. The experimental results show that the fuel-rich mixture produced by the gas generator would ignite rapidly in the solid scramjet combustor. The combustion process showed a typical characteristic of establishment-development-maintenance-attenuation. Compared to the flame-holding cavity, the other shapes of cavities, e.g., narrow and lobe, can improve mixing and combustion. In our experiment, the combustion efficiency increased from 0.41 to 0.48, and the total pressure recovery was 0.36. In summary, the proposed solid scramjet combustor can effectively solve the ignition delay problem of the fuel-rich mixture, and the narrow/lobe cavity shows the ability to improve the mixing and combustion of the fuel-rich mixture.
4 citations
TL;DR: In this article , a direct-connect experimented investigation of combustion modes transition was carried out, simulating inflow conditions of Mach number 6.0 and flight altitude 25 km, and the experimental pressure data were used to distinguish the combustion modes accurately.
2 citations
Cited by
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TL;DR: In this paper, the influence of three different injection structures on the performance of a solid scramjet was investigated using direct-connect tests using a boron-based fuel-rich propellant and simulated a flight Mach number 5.6 at 25 km.
8 citations
TL;DR: In this paper , the porosity was introduced into the Navier-Stokes equation, and a program suitable for solving gas-particle two-phase flow in the supersonic flow field was developed.
8 citations
TL;DR: In this article , the authors investigated the ignition and combustion characteristics of amorphous boron agglomerates under different oxygen concentrations in comparison with those of single-particle crystalline borons, and they indicated that ejection and explosion phenomena are likely to exist in the local highoxygen regions of the combustion chamber.
8 citations
TL;DR: In this article , a three-dimensional numerical investigation has been carried out on the performance and combustion characteristics of a scramjet combustor with and without cavity for various strut injector configurations.
4 citations
TL;DR: In this article, a modular solid scramjet combustor with multicavity was proposed, which can effectively solve the ignition delay problem of the fuel-rich mixture, and the narrow/lobe cavity shows the ability to improve the mixing and combustion of the mixture.
Abstract: In this paper, a modular solid scramjet combustor with multicavity was proposed. The influence of multicavity shape on the performance of solid scramjet was investigated by the direct-connected tests. The experiments simulated a flight Mach 5.5 at 25 km. The boron-based fuel-rich propellant was used. The microstructure of combustion products was analyzed by SEM. The experimental results show that the fuel-rich mixture produced by the gas generator would ignite rapidly in the solid scramjet combustor. The combustion process showed a typical characteristic of establishment-development-maintenance-attenuation. Compared to the flame-holding cavity, the other shapes of cavities, e.g., narrow and lobe, can improve mixing and combustion. In our experiment, the combustion efficiency increased from 0.41 to 0.48, and the total pressure recovery was 0.36. In summary, the proposed solid scramjet combustor can effectively solve the ignition delay problem of the fuel-rich mixture, and the narrow/lobe cavity shows the ability to improve the mixing and combustion of the fuel-rich mixture.
4 citations